GOE 113 AIRFOIL (goe113-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 113 AIRFOIL (goe113-il) Reynolds number: 200,000 Max Cl/Cd: 66.85 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe113-il-200000-n5.txt Download as CSV file: xf-goe113-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 113 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3298 0.08721 0.08400 -0.0167 1.0000 0.0205
-8.000 -0.3287 0.08384 0.08065 -0.0179 1.0000 0.0215
-7.750 -0.3283 0.08050 0.07735 -0.0192 1.0000 0.0220
-7.500 -0.3285 0.07716 0.07404 -0.0204 1.0000 0.0222
-7.250 -0.3300 0.07384 0.07077 -0.0215 1.0000 0.0223
-7.000 -0.3334 0.07068 0.06766 -0.0223 1.0000 0.0224
-6.750 -0.3356 0.06731 0.06434 -0.0237 1.0000 0.0224
-6.500 -0.3346 0.06357 0.06062 -0.0258 1.0000 0.0225
-6.250 -0.3317 0.05970 0.05677 -0.0279 1.0000 0.0225
-6.000 -0.3271 0.05570 0.05276 -0.0298 1.0000 0.0226
-5.750 -0.3210 0.05170 0.04874 -0.0314 1.0000 0.0226
-5.500 -0.3137 0.04767 0.04466 -0.0326 1.0000 0.0226
-5.000 -0.3061 0.05056 0.04695 -0.0402 1.0000 0.0116
-4.750 -0.2890 0.04627 0.04250 -0.0414 1.0000 0.0113
-4.500 -0.2693 0.04216 0.03821 -0.0424 1.0000 0.0111
-4.250 -0.2397 0.03756 0.03334 -0.0448 0.9980 0.0111
-4.000 -0.1982 0.03283 0.02818 -0.0479 0.9940 0.0124
-3.750 -0.1634 0.02814 0.02306 -0.0512 0.9894 0.0132
-3.500 -0.1270 0.02474 0.01925 -0.0534 0.9845 0.0137
-3.250 -0.0899 0.02213 0.01624 -0.0556 0.9796 0.0147
-3.000 -0.0544 0.02022 0.01396 -0.0571 0.9728 0.0176
-2.750 -0.0181 0.01781 0.01101 -0.0581 0.9658 0.0207
-2.500 0.0165 0.01624 0.00902 -0.0590 0.9570 0.0245
-2.250 0.0499 0.01519 0.00784 -0.0603 0.9463 0.0289
-2.000 0.0836 0.01436 0.00673 -0.0612 0.9337 0.0342
-1.750 0.1166 0.01338 0.00569 -0.0623 0.9187 0.0372
-1.500 0.1503 0.01285 0.00508 -0.0634 0.9008 0.0411
-1.250 0.1824 0.01221 0.00435 -0.0641 0.8785 0.0410
-1.000 0.2134 0.01171 0.00372 -0.0645 0.8527 0.0406
-0.750 0.2422 0.01136 0.00322 -0.0644 0.8228 0.0404
-0.500 0.2695 0.01115 0.00284 -0.0640 0.7933 0.0404
-0.250 0.2961 0.01104 0.00252 -0.0635 0.7657 0.0406
0.000 0.3228 0.01099 0.00228 -0.0631 0.7414 0.0412
0.250 0.3495 0.01098 0.00209 -0.0627 0.7190 0.0423
0.500 0.3761 0.01098 0.00194 -0.0623 0.6966 0.0449
1.000 0.4258 0.00867 0.00191 -0.0610 0.6547 1.0000
1.250 0.4522 0.00884 0.00191 -0.0606 0.6333 1.0000
1.500 0.4786 0.00902 0.00193 -0.0603 0.6127 1.0000
1.750 0.5049 0.00919 0.00196 -0.0600 0.5904 1.0000
2.000 0.5312 0.00938 0.00202 -0.0597 0.5695 1.0000
2.250 0.5578 0.00955 0.00212 -0.0594 0.5495 1.0000
2.500 0.5843 0.00973 0.00222 -0.0592 0.5303 1.0000
2.750 0.6109 0.00991 0.00234 -0.0590 0.5135 1.0000
3.000 0.6376 0.01009 0.00248 -0.0588 0.4963 1.0000
3.250 0.6642 0.01027 0.00267 -0.0586 0.4767 1.0000
3.500 0.6904 0.01049 0.00285 -0.0583 0.4541 1.0000
3.750 0.7166 0.01072 0.00305 -0.0581 0.4259 1.0000
4.000 0.7404 0.01122 0.00326 -0.0575 0.3552 1.0000
4.250 0.7613 0.01220 0.00371 -0.0568 0.2538 1.0000
4.500 0.7849 0.01288 0.00416 -0.0564 0.2089 1.0000
4.750 0.8094 0.01343 0.00456 -0.0560 0.1674 1.0000
5.000 0.8314 0.01438 0.00510 -0.0555 0.1012 1.0000
5.250 0.8514 0.01577 0.00613 -0.0544 0.0186 1.0000
5.500 0.8757 0.01645 0.00698 -0.0538 0.0149 1.0000
5.750 0.8994 0.01726 0.00800 -0.0530 0.0132 1.0000
6.000 0.9214 0.01835 0.00935 -0.0520 0.0114 1.0000
6.250 0.9442 0.01917 0.01034 -0.0512 0.0102 1.0000
6.500 0.9649 0.02030 0.01164 -0.0501 0.0096 1.0000
6.750 0.9841 0.02162 0.01313 -0.0488 0.0092 1.0000
7.000 1.0026 0.02309 0.01471 -0.0474 0.0089 1.0000
7.250 1.0213 0.02472 0.01644 -0.0459 0.0086 1.0000
7.500 1.0402 0.02636 0.01815 -0.0447 0.0080 1.0000
7.750 1.0572 0.02871 0.02050 -0.0436 0.0071 1.0000
8.000 1.0759 0.03124 0.02321 -0.0423 0.0065 1.0000
8.250 1.0949 0.03334 0.02558 -0.0410 0.0064 1.0000
8.500 1.1120 0.03575 0.02830 -0.0396 0.0064 1.0000
8.750 1.1265 0.03845 0.03132 -0.0380 0.0063 1.0000
9.000 1.1380 0.04142 0.03470 -0.0361 0.0064 1.0000
9.250 1.1459 0.04466 0.03829 -0.0342 0.0064 1.0000
9.500 1.1500 0.04821 0.04217 -0.0321 0.0065 1.0000
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Polar data table (+)
Polar graphs
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